Longitudinal Aerodynamic Coefficients Estimation and Identifiability Analysis for Hypersonic Glider Controlled by Moving Mass

  • Pengxin Wei
  • Changsheng GaoEmail author
  • Wuxing Jing
Original Paper


This paper presents a composite Bank-To-Turn (BTT) control mode with a moving mass and non-redundant Reaction Control System (RCS) for a hypersonic unpowered glider vehicle. This type of control mode can not only preclude the aerodynamic control surfaces ablation, but also optimize the internal space of flight vehicle. The identification of the aerodynamic coefficients for gliders under the novel control mode remains an important research focus. As a key part of system identification, input design greatly affects the identification results. Taking into account the flight characteristics and composite control strategy, the longitudinal dynamic characteristics considering the cubic nonlinearities of hypersonic glider are analyzed and the motion form of internal moving mass is designed based on multi-sine input method. The identifiability and identifiability degree of each longitudinal parameter are evaluated using singular value decomposition of the measure matrix. Simulation results demonstrate that the designed input form improves the accuracy of the estimated parameters, and show the identification order from the most identifiable parameter to the least identifiable parameter.


Hypersonic glider Moving mass control Input design Identifiability analysis 


\( \alpha \)

Angle-of-attack (AOA), deg

\( \beta \)

Sideslip angle, deg

\( \phi \)

Roll angle, deg

\( \theta \)

Pitch angle, deg

\( \psi \)

Yaw angle, deg

\( L \)

Reference length, m

\( S_{B} \)

Cross-sectional area, m2

\( \omega_{x} \)

Roll angular velocity, rad/s

\( \omega_{y} \)

Yaw angular velocity, rad/s

\( \omega_{z} \)

Pitch angular velocity, rad/s

\( v \)

Magnitude of inertial velocity vector, m/s

\( q \)

Dynamic pressure, kg/(m s2)

\( \rho \)

Air density, kg/m3

\( I_{x} \)

Moments of inertia about x-body axes, kg/(m s2)

\( I_{y} \)

Moments of inertia about y-body axes, kg/(m s2)

\( I_{z} \)

Moments of inertia about z-body axes, kg/(m s2)

\( \delta \)

Displacement of moving mass along the rail, m

\( \dot{\delta } \)

Velocity of the moving mass along the rail, m/s

\( \ddot{\delta } \)

Acceleration of the moving mass, m/s2

\( l \)

Axial coordinate of the moving mass in body frame, m

\( m_{\text{p}} \)

Mass of the moving mass, kg

\( m_{\text{S}} \)

Mass of the system, kg

\( \mu \)

Ratio of the moving mass relative to the system

\( C_{x} \)

Aerodynamics drag coefficient

\( C_{y}^{\alpha } \)

Partial derivatives of the normal forces coefficients with respect to AOA

\( C_{z}^{\beta } \)

Partial derivatives of the normal forces coefficients with respect to sideslip angle

\( m_{x}^{i} \)

Rolling moment coefficients derivatives attributable to i, \( i = \beta ,{\kern 1pt} {\kern 1pt} \omega_{x} ,{\kern 1pt} {\kern 1pt} \omega_{y} \)

\( m_{y}^{i} \)

Yaw moment coefficients derivatives attributable to i, i = \( \beta ,{\kern 1pt} {\kern 1pt} \omega_{x} ,{\kern 1pt} {\kern 1pt} \omega_{y} \)

\( m_{z}^{i} \)

Pitch moment coefficients derivatives attributable to i, i = \( \alpha ,{\kern 1pt} {\kern 1pt} \omega_{z} \)



This work was supported by the National Natural Science Foundation of China (NNSFC) through Grant nos. 10902026 and 11572097. The first author was also supported by the China Scholarship Council (CSC) under Grant 201406120080.


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Copyright information

© The Korean Society for Aeronautical & Space Sciences 2019

Authors and Affiliations

  1. 1.Department of Aerospace EngineeringHarbin Institute of TechnologyHarbinChina
  2. 2.Automation Engineering Center, Research Institute of China Shipbuilding Industry CorporationHarbinChina

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